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14,750 pounds (6,690 kg) total per tank.
OPERATING MANUAL
2A-28-00 PRODUCTION AIRCRAFT SYSTEMS
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October 11/01
Revision 5
During gravity fueling, fuel is allowed to travel inboard, through the ribs, to
the aircraft centerline. This path fills the aircraft from the centerline rib,
including the hopper, outboard.
A grounding wire receptacle is incorporated in to the wing leading edge so
that the gravity fueling nozzle may be grounded during fueling. Gulfstream
recommends gravity fueling take place over the leading edge of the wing,
rather than the trailing edge. Procedures for over-wing (gravity) fueling are
presented in Chapter 9: Handling and Servicing.
3. Limitations:
A. Usable Fuel Capacities:
Left Tank Right Tank Total
14,750 lb (6,690 kg) 14,750 lb (6,690 kg) 29,500 lb (13,380 kg)
2,185 gal (8,271 L.) 2,185 gal (8,271 L.) 4,370 gal (16,542 L.)
NOTE:
It is possible to upload fuel in excess of 29,500 lb. This
is permitted as long as the maximum ramp weight and
/ or the maximum takeoff weight is not exceeded, and
the loaded aircraft center of gravity is within limits.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-28-00
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OPERATING MANUAL
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2A-28-00 PRODUCTION AIRCRAFT SYSTEMS
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Fuel Hopper Simplified
Block Diagram
Figure 3
OPERATING MANUAL
2A-28-00
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October 11/01
2A-28-30: Fuel Distribution System
1. General Description:
The fuel distribution system moves fuel from the wing fuel tanks to refill the
hoppers and delivers fuel under pressure from the hoppers to the engines and
APU.
Additionally, the fuel distribution system allows fueling and suction defueling
through a single-point pressure fueling adapter. Defueling can also be
accomplished using the boost pumps, drains or a combination of all three
methods.
The fuel distribution system is composed of the following subsystems, units and
components:
• Pressure Fueling System
• Defueling System
• Fuel Boost Pumps
• Fuel Ejectors
• Fuel Shutoff Valves
2. Description of Subsystems, Units and Components:
A. Pressure Fueling System:
The single-point pressure fueling system, shown in Figure 1 and Figure 4,
is a hydromechanical system. It is capable of control from the cockpit (by
solenoid valves) or from the adapter (by manual shutoff means).
Components of the system include:
• Pressure fueling adapter
• Two precheck valves
• Two shutoff valves
• Two sensing valves
• Four high-level pilot valves
• Two fuel shutoff solenoid valves
(1) Connection and Commencement:
The fueling adapter is located underneath the right wing leading
edge wing-to-fuselage fillet. After connecting the fuel nozzle to the
fueling adapter, opening the nozzle supplies fuel at 35 to 55 psig
(optimum for adequate prechecks) to the pressure fueling shutoff
valve. Fuel pressure against the shutoff valve forces the poppet
open, allowing fuel to flow to the tanks. Once fueling commences,
system prechecks are completed.
(2) Precheck Selector To FLOAT:
With a tank’s precheck selector in FLOAT, fuel flows through sense
lines into the inboard and outboard high-level pilot valve float
chambers. Flow is such that it flows into the chambers faster than it
can drain through openings in the bottom of the chambers. As pilot
valve fuel level rises, the float in each valve rises until it closes the
valve’s poppet. The resulting back pressure in the inboard and
outboard sense lines overcomes fuel pressure against the shutoff
valve, which then closes to stop fueling. This sequence indicates a
successful test.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-28-00
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October 11/01
Revision 5
(3) Precheck Selector To TANK PRESS:
Placing the precheck selector to TANK PRESS directs fuel to the
tank pressure sense valve. Back pressure in the sense line then
overcomes fuel pressure against the shutoff valve, which then
closes to stop fueling. This sequence indicates a successful test.
(4) Precheck Selector To FUEL:
Placing the precheck selector to FUEL between each test sequence
enables continued testing. After completion of the tests, placing the
precheck selector to FUEL resumes normal fueling.
(5) Full Load Fueling:
As the fuel level rises, the inboard high-level pilot valves fills through
the opening in the bottom of its chamber and closes before the
　
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